KR102099307B1 - Turbulence generating structure for enhancing cooling performance of liner and a gas turbine combustor using the same - Google Patents

Abstract

The present invention relates to a turbulence generating structure that promotes liner cooling for improving transition piece cooling performance, and a combustor for a gas turbine comprising the same, in detail applied to a side portion of a dual structure consisting of a liner and a flow sleeve for cooling a duct assembly As a liner cooling structure, a plurality of ribs are arranged to protrude along the axial direction on the surface of the liner, and the ribs are formed to protrude blocks at regular intervals along the axial direction to provide cooling holes between the blocks. The first flow path gap between any one rib is formed wider than the second flow path gap adjacent to the first flow path gap, and the first flow path gap and the second flow path gap are repeatedly arranged along the radial direction to compress compressed air for cooling. Turbulent flow generation is provided to allow mutual penetration into the low pressure flow path, thereby limiting cooling. A turbulence generating structure that promotes liner cooling with increased liner cooling efficiency, which can avoid pressure drop while generating optimal turbulence that can maximize the residence time and cooling area on the liner surface using air, and It relates to a combustor for a gas turbine including this.

Description

Turbine generation structure that promotes liner cooling and gas turbine combustor including the same TECHNICAL STRUCTURE FOR ENHANCING COOLING PERFORMANCE OF LINER AND A GAS TURBINE COMBUSTOR USING THE SAME

The present invention relates to a gas turbine, and more particularly, to a duct assembly structure for promoting film cooling of a liner applied to a combustor for a gas turbine.

The gas turbine combustor is provided between the compressor and the turbine, and mixes compressed air supplied from the compressor with fuel to equalize pressure to produce a high-energy combustion gas, and sends it to a turbine that converts thermal energy of the combustion gas into mechanical energy. Perform.

Such a combustor is provided with a duct assembly composed of a liner in direct contact with high-temperature combustion gas and a flow sleeve surrounding it, and a transition piece or the like is essential for proper cooling, so for this purpose, part or all of the compressed air flowing out of the compressor is flow sleeve It penetrates into the annular space part inside through the inlet hole of to promote cooling of the liner (see FIG. 2).

In particular, as the ignition and combustion progress inside the liner, the hot combustion gas H flows downstream, so that the surface of the liner is continuously exposed to the high temperature environment. On the other hand, the compressed air for cooling forms a flow for cooling the film through a side portion wrapped with a liner and a flow sleeve (see FIG. 3). In particular, the surface of the rear liner to which the elastic support means (seal: seal) is coupled has poor cooling performance, thereby forming a separate flow path between the seal and the combustion chamber through the inlet hole formed on the surface (see FIG. 4).

However, according to the surface structure for cooling the liner in the related art, the flow of compressed air induced from the inlet hole of the flow sleeve is simple, and particularly, the flow path to the inside of the rear liner is the same, so it can be exerted using limited compressed air. There was a problem that could not reach the maximum possible cooling efficiency.

The present invention is to solve the above problems, by using the limited cooling air supplied from the compressor to create an optimal turbulence that can maximize the residence time and cooling area on the surface of the liner, while avoiding the pressure drop. It is an object to provide a combustor for a gas turbine including a turbulent flow generating structure and an improved liner cooling efficiency.

A turbulence generating structure that promotes liner cooling according to the present invention for achieving the above object and a combustor for a gas turbine comprising the same, liner cooling applied to a side portion of a dual structure composed of a liner and a flow sleeve for cooling the duct assembly As a structure, a plurality of ribs are arranged to protrude along the axial direction on the surface of the liner, and the ribs are formed to protrude blocks at regular intervals along the axial direction to provide cooling holes between the blocks, and any one adjacent rib The first flow path interval between is formed to be wider than the second flow path interval adjacent to the first flow path interval, and the first flow path interval and the second flow path interval are repeatedly arranged along the radial direction, thereby compressing compressed air for cooling. It characterized in that it comprises a first turbulence generating unit provided to be mutually penetrated into the low flow path.

In addition, the first turbulence generating unit is characterized in that the front and rear surfaces of the block formed on the rib are inclined so that the flow path formed by the cooling hole is guided in a diagonal direction.

In addition, the inclined surface of the block is characterized in that it is formed to be symmetrical about the first flow path spacing or the second flow path spacing.

In addition, the inclined surface of the block is characterized in that it forms an acute angle with respect to the axial direction.

In addition, the first turbulence generating unit is characterized in that the first flow path spacing and the second flow path spacing are variable along the axial direction.

In addition, a notch is formed in the rib so that the first flow path spacing and the second flow path spacing are variable in the second flow path spacing and the first flow path spacing, respectively, along the axial direction.

In addition, the block is arranged to protrude blocks at regular intervals along the radial direction on the surface of the liner, and the blocks are provided to intersect with each other along the axial direction and include a second turbulence generating unit provided with a cooling space between the blocks. Is done.

In addition, the second turbulence generating unit is formed so that the front and rear surfaces of the block are inclined, and the flow path formed by the cooling space is guided in a diagonal direction.

In addition, it is characterized in that the blocks arranged along the radial direction are formed at predetermined intervals so that the flow path between the ribs provided in the first turbulence generating unit leads to the second turbulence generating unit.

In addition, the second turbulence generating unit, characterized in that the chamfer is formed in the corner of the block.

In addition, the second turbulence generating unit, characterized in that the chamfer is formed only on the front surface of the block.

In addition, the chamfer is characterized in that it is formed of a curved surface.

In addition, the surface of the liner is characterized in that the first turbulent flow generator and the second turbulent flow generator are sequentially provided according to the flow of compressed air for cooling.

In addition, the rear liner surface is characterized in that the first turbulence generating portion and the second turbulence generating portion are sequentially provided.

In addition, the first turbulence generator and the second turbulence generator are characterized in that the flow rate and flow rate of the compressed air for cooling are bounded by variables.

In addition, the surface of the liner is arranged to protrude the pins in the axial and radial directions, it characterized in that it comprises a third turbulence generating portion is provided with a cooling space between the fins.

In addition, the surface of the liner is characterized in that the first turbulence generator, the second turbulence generator and the third turbulence generator are selectively and sequentially provided according to the flow of compressed air for cooling.

In addition, the rear liner surface is characterized in that the first turbulence generating portion, the second turbulence generating portion and the third turbulence generating portion are provided selectively and sequentially.

By applying the turbulence generating structure that promotes the cooling of the liner of the present invention to a duct assembly and a gas turbine combustor including the same, residence time and cooling area on the surface of the liner are generated by generating optimal turbulence with limited compressed air supplied from the compressor of the gas turbine. It has the advantage of maximizing and minimizing the pressure drop to increase the overall liner cooling efficiency.

In particular, by providing a turbulent flow generation structure optimized for flow rate and flow rate with limited cooling compressed air introduced into the rear liner surface having poor cooling performance, there is an advantage of performing intensive cooling on the inside of the liner in which the seal is coupled.

However, the effects of the present invention are not limited to the above-mentioned effects, and other effects not mentioned will be clearly understood by those skilled in the art from the following description.

1 is a view showing the overall structure of a gas turbine.
2 is a view for explaining the introduction of compressed air for cooling and combustion of a conventional gas turbine.
3 is a view showing the flow of compressed air for cooling of a conventional liner and a flow sleeve surrounding it.
4 is a view showing the flow of compressed air for cooling of the rear surface of a liner to which a conventional elastic support means is coupled.
5 is a view showing an embodiment of a turbulence generating unit according to a turbulence generating structure that promotes cooling of the liner according to the present invention.
6 is a view showing another embodiment of a turbulence generating unit according to a turbulence generating structure that promotes cooling of the liner according to the present invention.
7 is a view showing another embodiment of a turbulence generating unit according to a turbulence generating structure that promotes cooling of the liner according to the present invention.
8 (a) and 8 (b) are layout views for explaining an embodiment of the first turbulence generation unit and the second turbulence generation unit according to the turbulence generation structure that promotes cooling of the liner according to the present invention.
9 is a view showing another embodiment of the second turbulence generating unit according to the turbulence generating structure that promotes cooling of the liner according to the present invention.
10 to 12 is a view showing another embodiment of the second turbulence generating unit according to the turbulence generating structure to promote the inventors liner cooling.
13 is a view showing an embodiment of a third turbulence generating unit according to a turbulence generating structure that promotes cooling of the liner according to the present invention.
14 is a conceptual view showing the arrangement of the turbulence generating parts according to the turbulence generating structure that promotes cooling of the liner according to the present invention.
15 (a) and 15 (b) are conceptual diagrams showing an embodiment of the arrangement of the turbulence generating unit according to the turbulence generating structure that promotes cooling of the liner according to the present invention.
16 is a view according to an embodiment of the front surface of the liner to which the present invention is applied with a turbulence generating structure that promotes cooling of the liner.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

In describing the embodiments of the present invention, descriptions of well-known structures that will be apparent to those skilled in the art will be omitted so as not to obscure the subject matter of the present invention. In addition, in adding the reference numerals to the components of each drawing, the same reference numerals will be assigned to the same components, even if they are displayed on different drawings, and when referring to the drawings, the thickness or configuration of the lines shown in the drawings It should be considered that the size of the elements may be exaggerated for clarity and convenience of explanation.

And, in describing the components of the embodiments of the present invention, terms such as first, second, A, B, (a), (b), and the like can be used. These terms are only for distinguishing the component from other components, and the nature, order, or order of the component is not limited by the term. When a component is described as being "connected", "coupled" or "connected" to another component, the component may be directly connected to or connected to the other component, but another component between each component It should also be understood that intervening may be indirectly "connected", "coupled" or "connected".

The thermodynamic cycle of the gas turbine ideally follows the Brayton cycle. The Brighton cycle consists of four processes: isoentropy compression (thermal compression), constant pressure rapid expansion, isoentropy expansion (thermal expansion), and constant pressure heat dissipation. That is, after inhaling atmospheric air and compressing it at a high pressure, the fuel is burned in a static pressure environment to release thermal energy, and this high-temperature combustion gas is expanded and converted into kinetic energy, and then exhaust gas containing residual energy is released into the atmosphere. . That is, the cycle consists of four processes: compression, heating, expansion, and heat dissipation.

The gas turbine that realizes the above Brayton cycle includes a compressor, a combustor, and a turbine. 1 is a view schematically showing the overall configuration of a gas turbine 1000. Although the following description will refer to FIG. 1, the description of the present invention can be widely applied to a turbine engine having a configuration equivalent to the gas turbine 1000 exemplarily illustrated in FIG. 1.

The compressor 1100 of the gas turbine 1000 is a part that plays a role of inhaling and compressing air and supplies air for combustion to the combustor 1200 while air for cooling to a high temperature region where cooling is required in the gas turbine 1000 The main role is to supply. Since the intake air undergoes an adiabatic compression process in the compressor 1100, the pressure and temperature of the air passing through the compressor 1100 rises. The compressor 1100 in the large gas turbine 1000 as shown in FIG. 1 is composed of a multi-stage axial compressor and compresses a large amount of air up to a target compression ratio through each stage.

Then, the combustor 1200 mixes the compressed air supplied from the outlet of the compressor 1100 with the fuel to equalize pressure to produce high-energy combustion gas. 2 shows an example of the combustor 1200 provided in the gas turbine 1000. The combustor 1200 is disposed downstream of the compressor 1100, and a plurality of burners 1220 are disposed along the annular combustor casing 1210. Each burner 1220 is provided with several combustion nozzles 1230, and fuel injected from the combustion nozzles 1230 is mixed with air in an appropriate ratio to achieve a state suitable for combustion.

The gas turbine 1000 may be a gas fuel and a liquid fuel, or a combination fuel combined with them. It is important to create a combustion environment to reduce the amount of exhaust gas, such as carbon monoxide and nitrogen oxide, which are the subject of legal regulation. Although the combustion control is relatively difficult, the advantage of being able to reduce the exhaust gas by reducing the combustion temperature and making uniform combustion is important. Therefore, a lot of premixed combustion is applied in recent years.

In the case of premixed combustion, compressed air is mixed with fuel injected from the combustion nozzle 1230 and then enters the combustion chamber 1240. The initial ignition of the premixed gas is performed using an igniter, and when combustion is stabilized, combustion is maintained by supplying fuel and air.

Since the combustor 1200 forms the highest temperature environment in the gas turbine 1000, proper cooling is required. In particular, in the gas turbine 1000, the turbine inlet temperature (TIT) is very important, because in general, the higher the turbine inlet temperature, the higher the efficiency of the gas turbine 1000. In addition, the higher the turbine inlet temperature, the more favorable the gas turbine combined power generation. For this reason, when classifying (class) the gas turbine 1000, it is also based on the turbine inlet temperature.

In order to increase the inlet temperature of the turbine, the temperature of the combustion gas must eventually be increased, so that the material of the duct assembly forming the flow path and the combustion chamber 1240 of the combustor 1200 through which the high temperature combustion gas flows has strong heat resistance. Of course, a design that can cool well is important.

Referring to FIG. 2, a duct assembly connecting a burner 1220 and a turbine 1300 to flow high-temperature combustion gas, that is, a duct assembly composed of a liner 1250 and a transition piece 1260 and a flow sleeve 1270 Compressed air flows along the outer surface of and is supplied to the combustion nozzle 1230, and in this process, the duct assembly heated by the hot combustion gas is appropriately cooled.

The duct assembly consists of a double structure in which the flow sleeve 1270 wraps the outside of the liner 1250 and the transition piece 1260 connected by the elastic support means 1280, and the compressed air is annular inside the flow sleeve 1270 It penetrates into the space to cool the liner 1250 and the transition piece 1260.

The liner 1250 is a tube member connected to the burner 1220 of the combustor 1200, and the space inside the liner 1250 forms the combustion chamber 1240. Then, the transition piece 1260 connected to the liner 1250 is connected to the inlet of the turbine 1300 serves to induce high temperature combustion gas to the turbine 1300. The flow sleeve 1270 protects the liner 1250 and the transition piece 1260 while preventing hot heat from being directly discharged to the outside.

In particular, since the liner 1250 and the transition piece 1260 are in direct contact with the hot combustion gas, proper cooling is essential. Basically, the liner 1250 and the transition piece 1260 are protected from high temperature combustion gas through film cooling using compressed air. For example, as shown in FIG. 2, a complex double-wall structure for introducing compressed air directly into the inner circumferential surfaces of the liner 1250 and the transition piece 1260 is also taken for effective film cooling.

And, since each end of the liner 1250 and the transition piece 1260 is fixed to the combustor 1200 and the turbine 1300, respectively, the elastic support means 1280 can accommodate length and diameter extension due to thermal expansion. The structure should be able to support the liner 1250 and the transition piece 1260.

The high-temperature, high-pressure combustion gas produced by the combustor 1200 is supplied to the turbine 1300 through a duct assembly. In the turbine 1300, thermal energy of the combustion gas is converted into mechanical energy in which the rotation shaft rotates by impinging and repelling a plurality of blades radially disposed on the rotation shaft of the turbine 1300 while the combustion gas expands adiabatically. A portion of the mechanical energy obtained from the turbine 1300 is supplied as energy necessary for compressing air in a compressor, and the rest is utilized as effective energy such as generating electric power by driving a generator.

Since the gas turbine 1000 has no reciprocating parts such as a piston-cylinder because the main components do not reciprocate, consumption of lubricant is extremely low, and the amplitude characteristic of reciprocating machines is greatly reduced, and high-speed motion is possible. There are advantages.

And, the thermal efficiency in the Brayton cycle increases because the higher the compression ratio for compressing air, and the higher the temperature (turbine inlet temperature) of the combustion gas flowing through the isentropic expansion process as described above, the gas turbine 1000 Also developed in the direction of increasing the compression ratio and the temperature at the inlet of the turbine 1300.

Hereinafter, with reference to FIGS. 2 to 16, a turbulence generating structure that promotes cooling of the liner according to the present invention applied to the combustor 1200 and the duct assembly of the gas turbine 1000 will be described in detail.

2 to 4 is a view illustrating the introduction of the compressed air for cooling and combustor of a conventional gas turbine, Figure 3 is a view showing the flow of the compressed air for cooling of the conventional liner and the flow sleeve surrounding it, Figure 4 It is a view showing the flow of compressed air for cooling of the surface of the rear liner 1252 in which a conventional seal is coupled.

Referring to this, the combustor is provided with a duct assembly composed of a liner 1250 directly contacting the high temperature combustion gas and a flow sleeve 1270 surrounding the same, and the transition piece 1270 and the like are essential for proper cooling. A part or all of the compressed air (A) flowing out of the air is penetrated into the inner annular space through the inlet hole of the flow sleeve to cool the liner (1250).

In particular, as the ignition and combustion progress inside the liner 1250, the hot combustion gas H flows downstream, so that the surface of the liner 1250 is continuously exposed to a high temperature environment. On the other hand, the compressed air for cooling (A) forms a flow for cooling the film through a side portion surrounded by a liner and a flow sleeve. In particular, referring to FIG. 4, the surface of the rear liner 1252 in which the seal, which is an elastic support means, is coupled has poor cooling performance, and thus a separate flow path between the chamber and the combustion chamber through the inlet hole 1263 formed in the surface ( A2).

The present invention is to improve the surface structure for cooling such a conventional liner, and in particular, it uses a limited compressed air by improving a simple flow path of compressed air derived from the inlet hole of the flow sleeve and a flow path introduced into the rear liner. This is to provide a turbulence generating structure capable of exerting the maximum cooling efficiency.

5 to 7 is a view showing the entire embodiment of the first turbulence generating unit (S10) according to the turbulence generation structure to promote the inventors liner cooling.

Referring to this, the present invention relates to a gas turbine combustor 1200 and a turbulence generating structure that promotes liner cooling that can be applied to a duct assembly provided therein, in detail, the combustor 1200 includes a transition piece 1260, It comprises a duct assembly consisting of a liner 1260 connected via the transition piece 1260 and an elastic support means 1280 and a fluid sleeve 1270 surrounding the transition piece 1270 and the liner 1250, The present invention relates to a liner cooling structure applied to a side portion of a dual structure consisting of a front liner 1251 or a rear liner 1252 which is a seal-coupled portion and a flow sleeve 1271.

In addition, the turbulence generation structure according to the present invention includes the first turbulence generation unit S10 shown in FIGS. 5 to 7, and the second turbulence generation unit S20 and the third turbulence generation unit S30 to be described later. It may further include, and constitutes a turbulence generating structure of the entire liner 1250 by a combination of the turbulence generating units S10, S20, and S30.

First, referring to the first turbulence generating unit S10 (see FIG. 5), it is arranged to protrude a plurality of ribs 100 along the axial direction X on the surface of the liner 1250, and the ribs 100 ), The block 120 is formed to protrude more at regular intervals along the axial direction X, and a cooling hole 130 is provided between the blocks 120.

Here, the first flow path gap L1 between any one of the adjacent ribs 100a and 100b is formed wider than the first flow path gap L1 and the second flow path gap L2 adjacent to it. That is, the first rib 100a and the second rib 100b are disposed adjacent to each other, but the first flow path gap L1, which is an interval therebetween, is the third rib disposed adjacent to the second rib 100b ( It is formed wider than the second flow path interval (L2) that is the interval between 100c).

In addition, the first flow path spacing L1 and the second flow path spacing L2 are repeatedly arranged along the radial direction, so that the compressed air for cooling may be provided to penetrate into the low pressure flow path.

Specifically, since the compressed air for cooling in the first flow path gap L1 having a relatively wide gap increases in pressure instead of decreasing the flow velocity, the turbulent flow due to an artificial pressure difference with the adjacent second flow path gap L2 is prevented. Will occur. That is, the compressed air in the first flow path interval L1 causes a cooling action along the axial direction, and at the same time, passes through the cooling hole 130 and is transferred to the adjacent second flow path interval L2 to maximize turbulence. .

The first turbulence generator S10 may be embodied in the following various embodiments.

Referring to FIG. 6, the front and rear surfaces of the block 121 formed on the rib 100 are formed to be inclined, and a flow path formed by the cooling hole 131 may be guided in a diagonal direction.

The inclined surface of the block 121 is formed to coincide with a constant pattern or a constant angle, so that the flow of the compressed air for auxiliary cooling along the diagonal direction can be formed independently of the flow of the compressed air along the axial direction.

Here, the inclined surface of the block is preferably to form a sufficient turbulence without forming a sharp acute angle with respect to the axial direction without significantly compromising the flow of compressed air along the axial direction, and more specifically, may be formed within 30 to 45 degrees. .

In another embodiment, the inclined surface of the block may be formed to be symmetric about the first flow path spacing L1 or the second flow path spacing L2 (see FIG. 6). The symmetry shape may be embodied to be formed along the path of the lateral turbulence in the adjacent second flow path spacing L2 on the basis of the first flow path spacing L1. In other words, the first ribs and the second ribs forming the second flow path gaps L2 to be collected in the axial direction X based on the second flow path gaps L2, respectively, have blocks 121a and 121b at regular intervals. ) Is formed to protrude, and the front and rear surfaces of the blocks 121a and 121b are inclined, and the flow paths formed by the cooling holes 131a and 131b are symmetrical to be collected in the axial direction (X). It can be guided in the diagonal direction.

Accordingly, the compressed air for cooling flowing in the first flow path gap L1 can be more easily penetrated into the flow path of the second flow path gap L2 having a low pressure, thereby contributing to the increase in turbulence.

Referring to FIG. 7, the first turbulence generating unit S10 may be formed such that the first flow path spacing L1 and the second flow path spacing L2 are variable along the axial direction X. Specifically, the first flow path spacing L1 and the second flow path spacing L2 along the axial direction X (refer to section S12-1 in FIG. 7), the second flow path spacing L2 and the second flow path, respectively. To be variable in the flow path spacing L1 (refer to area S12-2 in FIG. 7), the rib 122c may be formed in the rib.

According to this variation, the inclined direction of the front and rear surfaces of the blocks 122a and 122b is formed to be formed along the path of the lateral turbulence in the adjacent second flow path spacing L2 based on the first flow path spacing L1. They can be interchanged.

Accordingly, in the first turbulence generating unit S10, while inducing the turbulent flow in the adjacent second flow path spacing L2 while causing a cooling action along the axial direction, the first flow path spacing based on the axial direction ( By translating the properties of L1) and the second flow path spacing L2, it is possible to maximize the residence time and cooling area on the surface of the liner with limited compressed air.

8 (a) and 8 (b) are arrangement diagrams for explaining an embodiment of the first turbulence generating unit S10 and the second turbulence generating unit S20 according to the turbulence generation structure that promotes cooling of the liner according to the present invention, respectively. 9 is a view showing another embodiment of the second turbulence generation unit S20 according to the turbulence generation structure that promotes cooling of the liner according to the present invention.

Referring to this, the second turbulence generating unit (S20) is arranged to protrude the block 140 at regular intervals along the radial direction (based on FIG. 8, meaning up and down direction) on the surface of the liner 1250. , The blocks 140 may be provided to cross each other along the axial direction X, and a cooling space 230 may be provided between the blocks 120.

According to the embodiment of Fig. 8 (b), the front and rear surfaces of the block 140 are formed so that the flow of the compressed air for auxiliary cooling along the diagonal direction is formed independently of the flow of the compressed air along the axial direction (X). The flow path formed obliquely and formed by the cooling space 230 may be guided in a diagonal direction. In addition, as in the present embodiment, the flow path spacing between the ribs provided in the first turbulence generation unit S10 (see FIG. 8 (a)), along the radial direction to lead to the second turbulence generation unit S20. The blocks 140 to be arranged may be formed at predetermined intervals.

As described above, according to the turbulence generation structure of the second turbulence generation unit S20 (see FIG. 9), the flow rate or flow rate is lowered by generating or increasing the intersection turbulence in the compressed air for cooling along the axial direction (X). By forming a cooling structure suitable for, it is possible to increase the residence time and cooling area of the compressed air for overall cooling.

10 to 12 is a view showing another embodiment of the second turbulence generating unit (S20) according to the turbulence generating structure to promote the inventors liner cooling.

Referring to FIG. 10, a chamfer 142a may be formed at an edge portion of the block 142 of the second turbulence generating unit S20. Accordingly, while the residence time of the cross-section turbulence increases according to the arrangement of the block 142, it is possible to minimize side effects due to the pressure drop.

The chamfer may be formed only on the front surface of the block 142 in consideration of processing cost and the like, and as shown in the embodiment of FIG. 11, the front and rear surfaces of the block 143 may contribute to activation of cross-current turbulence in the cooling space 233 Since all the chamfers are formed, it can be provided as a rhombus-shaped block 143.

Referring to FIG. 12, the chamfer 144a may be formed as a curved surface. Specifically, the cooling space 234 may be provided such that the front surface of the chamfer 144a has a block 144 formed in a semicircle shape.

As described above, the second turbulence generation unit S20 forms a cooling structure optimized for a reduced flow rate or flow rate as the compressed air for cooling progresses, and thus the front liner 1251 is independent of the first turbulence generation unit S10. Or it can be applied to the rear liner 1252.

If considering the flow rate and flow rate of the compressed air for cooling through the entire liner 1250, the first turbulence generating unit (S10) and the second turbulence generating unit (S20) are provided on the surface of the liner according to the flow of the compressed air for cooling. It is preferably provided sequentially (see FIG. 14 to be described later).

Here, the axial direction (X) refers to a direction in which compressed air for cooling is drawn in from the induction sleeve 1270 and flows based on the central axis of the liner 1250. Accordingly, when the surface of the front liner 1251 is referenced, the first turbulence generating unit S10 and the second turbulence generating unit S20 may be sequentially provided from the rear side.

Specifically, the rear liner 1252 surface may also be provided with a first turbulence generating unit S10 and a second turbulence generating unit S20 sequentially, in the flow of compressed air for cooling (see A2 in FIG. 4). Accordingly, the first turbulence generator S10 and the second turbulence generator S20 may be sequentially provided from the front.

As described above, the first turbulent flow generator S10 and the second turbulent flow generator S20 are bounded by variables of the flow rate and flow rate of the compressed air for cooling, thereby generating optimal turbulent flow for cooling of the liner. With limited compressed air, cooling efficiency can be maximized.

In particular, the seals can be combined to provide a turbulence generating structure that realizes optimized cooling on the rear liner 1252 surface where cooling performance is poor.

13 is a view showing an embodiment of a third turbulence generating unit S30 according to a turbulence generating structure that promotes cooling of the liner according to the present invention.

Referring to this, on the surface of the liner 1250 of the third turbulence generating unit S30, fins 150 are arranged to protrude along the axial and radial directions, and a cooling space 240 is provided between the fins. It can be provided as possible.

Accordingly, by generating or increasing the turbulence at the cross section in response to the inevitable decrease in flow rate or flow rate according to the axial progression of the compressed air for cooling, it is possible to increase the overall residence time of the compressed air for cooling.

The third turbulence generator S30 forms a cooling structure optimized for a reduced flow rate or flow rate as the compressed air for cooling progresses, so that the first turbulence generator S10 or the second turbulence generator S20 It can be applied independently to the front liner 1251 or the rear liner 1252.

Specifically, the turbulence generating structure of the third turbulence generator S30 may be provided on the surface of the liner 1250 in response to compressed air for cooling at a reduced flow rate compared to the second turbulence generator S20.

Hereinafter, the arrangement structure on the surface of the liner 1250 of the first to third turbulence generating units S10, S20, and S30 will be described.

14 and 15 (a) and (b) is a conceptual diagram showing embodiments according to the arrangement of the turbulence generating unit according to the turbulence generating structure to promote the inventors liner cooling.

On the surface of the liner 1250, as described above, the first turbulence generating unit (S10), the second turbulence generating unit (S20), and the third turbulence generating unit (S30) are selectively selected according to the flow of compressed air for cooling. It may be provided sequentially.

The selective arrangement means that the first turbulence generation unit S10, the second turbulence generation unit S20, and the third turbulence generation unit S30 according to the flow of compressed air for cooling on the surface of the liner 1250 The arrangement order is maintained, but considering the degree of decrease in flow rate and flow rate and the axial length of the entire liner 1250, the first turbulence generation unit S10 and the third turbulence are excluded except for the second turbulence generation unit S20. It means that only the generator S30 may be sequentially provided.

Similarly, a first turbulence generator S10, a second turbulence generator S20 and a third turbulence generator S30 may be selectively and sequentially provided on the rear liner 1252 surface.

In addition, the first turbulence generator to the third turbulence generator (S10, S20, S30) may be bounded by variables of the flow rate and flow rate of the compressed air for cooling. Accordingly, the boundary line may be formed in a straight line, a curved line or a diagonal line according to a change in the flow rate and flow rate of the compressed air for cooling determined according to various factors such as size, type and material of the liner 1250 (FIG. 14) And Figure 15).

In addition, the length of the axial direction (X) of each turbulence generating unit may also be determined as variables of the flow rate and flow rate of compressed air for cooling the liner 1250.

Further, as shown in (b) of FIG. 15, a third turbulence generating unit S30 may be artificially inserted in the middle of the second turbulence generating unit S20 in consideration of a change in the flow rate or flow rate of the compressed air for cooling. You can.

According to the combination of the turbulence generating units (S10, S20, S30), it is possible to maximize the cooling efficiency with limited compressed air by generating optimal turbulence for cooling the liner as a whole.

16 is a view according to an embodiment of the front surface of the liner to which the present invention is applied with a turbulence generating structure that promotes cooling of the liner.

This embodiment relates to a turbulence generating structure in which the first turbulence generator S10 is applied to the front liner 1251.

Specifically, a plurality of ribs 100 are arranged to protrude in a spiral shape to have a constant angle with the axial direction X on the front liner 1251 surface, and the ribs 100 are constant along the rib direction. Blocks 120 are formed to protrude more at intervals, and cooling holes 130 may be provided between the blocks 120.

As described above, the plurality of ribs 100 are arranged in a diagonal direction (spiral direction relative to the liner surface) rather than in the axial direction (X), and the cooling hole 130 cools the axial direction (X) in compressed air for cooling. By being formed to be guided, it is possible to diversify the flow path of the surface of the liner 1250.

As described above, by applying the turbulence generating structure that promotes the cooling of the liner according to the present invention to a duct assembly and a combustor for a gas turbine including the same, the optimal turbulence is generated by the limited compressed air supplied from the compressor of the gas turbine, and the residence time at the liner surface By maximizing the cooling area and minimizing the pressure drop, it is possible to increase the overall liner cooling efficiency.

In particular, by providing a turbulence generating structure optimized for flow velocity and flow rate with limited cooling compressed air introduced into the rear liner surface having poor cooling performance, it is possible to perform intensive cooling on the inside of the liner where the seal is coupled.

In the above, a turbulence generating structure that promotes cooling of the liner for improving the cooling performance of the transition piece according to the present invention and a combustor for a gas turbine including the same have been described. It will be understood that the technical configuration of the present invention can be implemented in other specific forms by those skilled in the art to which the present invention pertains without changing the technical spirit or essential features of the present invention.

Therefore, the above-described embodiments are to be understood in all respects as illustrative and not restrictive.

100: rib 110: linear projection
120, 140: block 150: pin portion
210: first flow path 220: second flow path
1250: Liner 1260: Transition piece
1270: flow sleeve 1280: elastic support means
S10: first turbulence generating unit S20: second turbulence generating unit
S30: Third turbulence generating unit A: Compressed air
X: Axial ang: Angle

Claims (30)

A liner cooling structure applied to a side surface of a dual structure consisting of a liner and a flow sleeve for cooling the duct assembly:
A plurality of ribs are arranged to protrude along the axial direction on the surface of the liner, and the ribs are formed to protrude blocks at regular intervals along the axial direction to provide cooling holes between the blocks.
The first flow path gap between any adjacent ribs is different from the second flow path gap adjacent to the first flow path gap, and the first flow path gap and the second flow path gap are repeatedly arranged along the radial direction to compress compressed air for cooling. It includes a first turbulence generator provided to be mutually penetrated into the low pressure flow path,
Turbulent flow generation structure for promoting liner cooling, characterized in that a rib is formed in the rib so that the first flow path spacing and the second flow path spacing are varied along the axial direction to the second flow path spacing and the first flow path spacing, respectively.
According to claim 1,
The first turbulence generating unit,
Turbulent flow generation structure for promoting liner cooling, characterized in that the front and rear surfaces of the block formed on the rib are inclined so that the flow path formed by the cooling hole is guided in a diagonal direction.
According to claim 2,
The inclined surface of the block is formed to be symmetrical about the first flow path spacing or the second flow path spacing, turbulence generating structure to promote the liner cooling.
According to claim 2,
The inclined surface of the block is a turbulence generating structure that promotes liner cooling, characterized in that it forms an acute angle with respect to the axial direction.
delete delete According to claim 1,
Characterized in that the blocker is arranged to protrude blocks at regular intervals along the radial direction on the surface of the liner, and the blocks are provided to intersect with each other along the axial direction, and a second turbulence generating unit provided with a cooling space between the blocks. Turbulence generation structure that promotes liner cooling.
The method of claim 7,
The second turbulence generating unit,
A turbulence generating structure that promotes liner cooling, characterized in that the front and rear surfaces of the block are formed to be inclined so that the flow path formed by the cooling space is guided in a diagonal direction.
The method of claim 7,
A turbulence generating structure for promoting liner cooling, characterized in that blocks arranged along a radial direction are formed at predetermined intervals so that a flow path between the ribs provided in the first turbulence generating unit leads to a second turbulence generating unit.
The method of claim 7,
The second turbulence generating unit,
Turbulence generating structure to promote the cooling of the liner, characterized in that the chamfer is formed at the edge of the block.
The method of claim 10,
The second turbulence generating unit,
The chamfer is formed only on the front surface of the block, characterized in that the turbulence generating structure to promote liner cooling.
The method of claim 10,
The chamfer is a turbulence generating structure that promotes cooling of the liner, characterized in that formed in a curved surface.
The method of claim 7,
A turbulence generation structure for promoting liner cooling, characterized in that a first turbulent flow generator and a second turbulent flow generator are sequentially provided on the surface of the liner in accordance with the flow of compressed air for cooling.
The method of claim 13,
A turbulence generating structure for promoting liner cooling, characterized in that the rear liner surface is sequentially provided with a first turbulence generator and a second turbulence generator.
The method of claim 7,
The first turbulence generating portion and the second turbulence generating portion is a turbulence generating structure for promoting liner cooling, characterized in that the boundary of the flow rate and flow rate of the compressed air for cooling as variables.
The method of claim 7,
The liner surface is arranged to protrude the fins in the axial and radial directions, and the third turbulence generating structure for promoting the liner cooling, characterized in that it comprises a third turbulence generating portion is provided with a cooling space between the fins.
The method of claim 16,
A turbulence generation structure for promoting liner cooling, characterized in that the surface of the liner is selectively and sequentially provided with a first turbulence generation unit, a second turbulence generation unit, and a third turbulence generation unit according to the flow of compressed air for cooling.
The method of claim 17,
A turbulence generating structure for promoting liner cooling, characterized in that the rear liner surface is provided with a first turbulence generator, a second turbulence generator, and a third turbulence generator selectively and sequentially.
As a duct assembly provided in the combustor:
Transition pieces;
A liner connected via the transition piece and an elastic support means; And
It includes a flow sleeve surrounding the outside of the transition piece and the liner,
On the surface of the liner,
A plurality of ribs are arranged to protrude along the axial direction, and the ribs are formed to protrude blocks at regular intervals along the axial direction to provide cooling holes between the blocks.
The first flow path gap between any adjacent ribs is different from the second flow path gap adjacent to the first flow path gap, and the first flow path gap and the second flow path gap are repeatedly arranged along the radial direction to compress compressed air for cooling. It includes a turbulence generating portion provided to penetrate each other in a low pressure flow path,
The turbulence generating unit, the duct assembly characterized in that the ribs are formed in the rib so that the first flow path spacing and the second flow path spacing in the axial direction is variable to the second flow path spacing and the first flow path spacing, respectively.
The method of claim 19,
The turbulence generating unit,
Duct assembly characterized in that the front and rear surfaces of the block formed on the rib are inclined so that the flow path formed by the cooling hole is guided in a diagonal direction.
The method of claim 20,
The inclined surface of the block is a duct assembly characterized in that it is formed to be symmetrical about the first flow path spacing or the second flow path spacing.
The method of claim 20,
Duct assembly characterized in that the inclined surface of the block forms an acute angle with respect to the axial direction.
delete delete As a combustor for gas turbines:
Provided with a duct assembly,
The duct assembly,
Transition pieces;
A liner connected via the transition piece and an elastic support means; And
It includes a flow sleeve surrounding the outside of the transition piece and the liner,
On the surface of the liner,
A plurality of ribs are arranged to protrude along the axial direction, and the ribs are formed to protrude blocks at regular intervals along the axial direction to provide cooling holes between the blocks.
The first flow path gap between any adjacent ribs is different from the second flow path gap adjacent to the first flow path gap, and the first flow path gap and the second flow path gap are repeatedly arranged along the radial direction to compress compressed air for cooling. It includes a turbulence generating portion provided to penetrate each other in a low pressure flow path,
The turbulence generating unit, the combustor characterized in that the ribs are formed in the rib so that the first flow path spacing and the second flow path spacing in the axial direction is variable to the second flow path spacing and the first flow path spacing, respectively.
The method of claim 25,
The turbulence generating unit,
Combustor characterized in that the front and rear surfaces of the block formed on the rib are inclined so that the flow path formed by the cooling hole is guided in a diagonal direction.
The method of claim 26,
Combustor characterized in that the inclined surface of the block is formed to be symmetric about the first flow path spacing or the second flow path spacing.
The method of claim 26,
Combustor characterized in that the inclined surface of the block forms an acute angle with respect to the axial direction.
delete delete

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